[Federal Register Volume 70, Number 102 (Friday, May 27, 2005)]
[Rules and Regulations]
[Pages 30617-30621]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-10433]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-19753; Directorate Identifier 2002-NM-264-AD; 
Amendment 39-14104; AD 2005-11-02]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 767-200, -300, and -300F 
Series Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD), which applies to certain Boeing Model 767-200, -300, and -300F 
series airplanes. That AD currently requires inspections for fatigue 
cracking of the horizontal stabilizer pivot bulkhead, and repetitive 
inspections or other follow-on actions. That action also provides a 
permanent repair, which is optional for airplanes with no cracks, and, 
if accomplished, ends the repetitive inspections. For airplanes on 
which the permanent repair is not installed, this new AD requires 
repetitive inspections of the same and additional inspection locations 
at new inspection intervals; a one-time torque test; and related 
investigative and corrective actions. For airplanes on which the 
permanent repair is installed, this new AD would require repetitive 
inspections of the repaired area and, if necessary, corrective action. 
This AD is prompted by reports of loose tension bolts and crack 
indications in the fuselage skin. We are issuing this AD to find and 
fix fatigue cracking of the horizontal stabilizer pivot bulkhead and 
adjacent structure, which could result in loss of the horizontal 
stabilizer.

DATES: This AD becomes effective July 1, 2005.
    The incorporation by reference of Boeing Alert Service Bulletin 
767-53A0078, Revision 3, dated November 15, 2001; and Boeing Alert 
Service Bulletin 767-53A0078, Revision 4, dated September 26, 2002, as 
listed in the AD is approved by the Director of the Federal Register as 
of July 1, 2005.
    On May 24, 2001 (66 FR 23538, May 9, 2001), the Director of the 
Federal Register approved the incorporation by reference of Boeing 
Service Bulletin 767-53-0078, Revision 2, dated April 19, 2001.

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207.
    Docket: The AD docket contains the proposed AD, comments, and any 
final disposition. You can examine the AD docket on the Internet at 
http://dms.dot.gov, or in person at the Docket Management Facility 
office between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the U.S. 
Department of Transportation, 400 Seventh Street SW., room PL-401, 
Washington, DC. This docket number is FAA-2004-19753; the directorate 
identifier for this docket is 2002-NM-264-AD.

FOR FURTHER INFORMATION CONTACT: Suzanne Masterson, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
917-6441; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend part 39 of the

[[Page 30618]]

Federal Aviation Regulations (14 CFR part 39) with an AD to supersede 
AD 2001-09-13, amendment 39-12220 (66 FR 23538, May 9, 2001). The 
existing AD applies to certain Boeing Model 767-200, -300, and -300F 
series airplanes. The proposed AD was published in the Federal Register 
on December 1, 2004 (69 FR 69838). That action proposed to require, for 
airplanes on which the permanent repair is not installed, repetitive 
inspections of the same and additional inspection locations at new 
inspection intervals; a one-time torque test; and related investigative 
and corrective actions. For airplanes on which the permanent repair is 
installed, that action proposed to require repetitive inspections of 
the repaired area and, if necessary, corrective action.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments that have been 
submitted on the proposed AD.

Request To Revise Compliance Time

    Two commenters request that we revise the compliance language in 
paragraph (n) of the proposed AD to specify that the earlier-occurring 
threshold determines the compliance time.
    We agree that we inadvertently omitted the phrase ``whichever 
occurs first'' in paragraph (n)(1). We have revised the final rule 
accordingly.

Request To Include Grace Period

    One commenter, an operator, requests that we revise paragraph (n) 
of the proposed AD to add a grace period to the inspection threshold. 
The commenter reports that some of its airplanes could exceed the 
proposed thresholds and would consequently be grounded as of the 
effective date of the AD. The commenter recommends a grace period of 18 
months.
    We agree with the request. A substantial portion of the Model 767 
fleet has accumulated more than 25,000 total flight cycles, and the 
cited service bulletin (767-53A0078) for this AD was originally issued 
October 15, 1998--more than 72 months ago. Therefore, some airplanes 
indeed could have already exceeded the thresholds in proposed paragraph 
(n). We find that an 18-month grace period will provide an acceptable 
level of safety. We have revised the final rule accordingly by adding 
the grace period in new paragraph (n)(3).

Request To Clarify Certain Requirements

    One commenter, an operator, has no objections to the proposed AD 
but notes a potential discrepancy in certain requirements. The 
commenter states that paragraphs (l)(1)(ii) and (o) of the proposed AD 
would require inspection of airplanes that meet certain criteria in the 
service bulletin but does not specify any requirement for airplanes 
that do not meet those criteria. The commenter requests that we clarify 
the proposed AD to address this case.
    We agree that clarification might be necessary. Paragraph (l)(1)(i) 
of this AD is required for all airplanes; paragraph (l)(1)(ii) is an 
additional action for certain airplanes. Cracking cannot be reliably 
detected--using the inspections in paragraph (l)--at critical fastener 
locations hidden by external doublers, rub strips, or wear plates; 
therefore, the open-hole high frequency eddy current (HFEC) inspections 
are required only for those airplanes that meet those criteria. For 
those airplanes, the open-hole HFEC inspections are required in 
addition to the surface inspections (HFEC, low frequency eddy current, 
and detailed visual inspections) required by paragraph (l) of this AD. 
We have revised paragraphs (l)(1)(ii) and (o) of this final rule to 
include this information for clarification.

Request To Add Authorized Representative

    One commenter requests a revision to the section titled 
``Difference Between the Proposed AD and the Service Bulletin'' in the 
preamble of the proposed AD. The commenter requests that we include a 
reference to the Boeing Airworthiness Representative (AR) in addition 
to the Designated Engineering Representative (DER).
    We partially agree with the request. All active Boeing Company DERs 
on the Model 767 fleet have been converted to ARs. Although the 
referenced section of the preamble is not restated in a final rule, we 
have replaced the DER reference in paragraph (p)(3) of this final rule.

Request for Reformatting

    One commenter requests that we revise certain formatting for the 
paragraph designations in the proposed AD. Specifically, in the 
proposed requirement to ``[d]o all the actions in paragraph (l)(1),'' 
the commenter notes the potential confusion between the lower case 
letter ``L'' and the numeral ``1,'' and suggests that using italics 
could help the reader differentiate between the two forms.
    We agree that certain paragraph designations might be difficult to 
distinguish. However, the Federal Register, which is the medium for 
notifying the public of official agency actions (including ADs), 
establishes the formatting requirements for regulations. The proposed 
AD followed those formatting requirements. We have not changed the 
final rule regarding this issue.

Explanation of Additional Changes to Proposed AD

    We have identified the inspections in paragraph (l)(1) in this 
final rule as ``detailed'' and ``special detailed'' inspections. New 
Note 3 in this final rule defines a special detailed inspection.
    Boeing has received a Delegation Option Authorization (DOA). We 
have revised this final rule to delegate the authority to approve an 
alternative method of compliance for any repair required by this AD to 
the Authorized Representative for the Boeing DOA Organization rather 
than the Designated Engineering Representative (DER).

Conclusion

    We have carefully reviewed the available data, including the 
comments that have been submitted, and determined that air safety and 
the public interest require adopting the AD with the changes described 
previously. We have determined that these changes will neither increase 
the economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    This AD will affect about 699 airplanes worldwide. The following 
table provides the estimated costs for U.S. operators to comply with 
this AD.

[[Page 30619]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                            Average                                            Number of U.S.-
              Action                Work   labor rate       Parts        Cost per airplane        registered
                                   hours    per hour                                              airplanes
----------------------------------------------------------------------------------------------------------------
Inspection (required by AD 2001-       1          $65  None...........  $65 (per inspection  287.
 09-13).                                                                 cycle).
Inspection and torque check (new       4           65  None...........  $260 (per            287.
 action).                                                                inspection cycle).
Post-modification inspection (new      6           65  None...........  $390...............  Unknown (for those
 action).                                                                                     with permanent
                                                                                              repair per this AD
                                                                                              or AD 2001-09-13).
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD. See the ADDRESSES section for a location to 
examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing amendment 39-12220 (66 FR 
23538, May 9, 2001), and by adding the following new airworthiness 
directive (AD):

2005-11-02 Boeing: Amendment 39-14104. Docket No. FAA-2004-19753; 
Directorate Identifier 2002-NM-264-AD.

Effective Date

    (a) This AD becomes effective July 1, 2005.

Affected ADs

    (b) This AD supersedes AD 2001-09-13, amendment 39-12220.

Applicability

    (c) This AD applies to Boeing Model 767-200, -300, and -300F 
series airplanes, as listed in Boeing Alert Service Bulletin 767-
53A0078, Revision 4, dated September 26, 2002; certificated in any 
category.

Unsafe Condition

    (d) This AD was prompted by reports of loose tension bolts and 
crack indications in the fuselage skin. We are issuing this AD to 
find and fix fatigue cracking of the horizontal stabilizer pivot 
bulkhead and adjacent structure, which could result in loss of the 
horizontal stabilizer.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Requirements of AD 2001-09-13, Restated

Initial Inspections

    (f) Prior to the accumulation of 8,000 total flight cycles, or 
within 90 days after May 24, 2001 (the effective date of AD 2001-09-
13), whichever occurs later, perform detailed, surface high 
frequency eddy current (HFEC), and low frequency eddy current (LFEC) 
inspections, as applicable, for cracking of the forward and aft 
outer chord, aft mid chord, and upper and lower intercostals of the 
Station 1809.5 bulkhead. Do the inspections per Boeing Service 
Bulletin 767-53-0078, Revision 2, dated April 19, 2001; or Boeing 
Alert Service Bulletin 767-53A0078, Revision 3, dated November 15, 
2001.

    Note 1: For the purposes of this AD, a detailed inspection is: 
``An intensive visual examination of a specific structural area, 
system, installation, or assembly to detect damage, failure, or 
irregularity. Available lighting is normally supplemented with a 
direct source of good lighting at intensity deemed appropriate by 
the inspector. Inspection aids such as mirror, magnifying lenses, 
etc., may be used. Surface cleaning and elaborate access procedures 
may be required.''

Repetitive Inspections

    (g) For areas where no cracking is found during the inspection 
per paragraph (f) of this AD: Repeat the inspections in paragraph 
(f) thereafter at the intervals specified in paragraphs (g)(1) and 
(g)(2) of this AD, per Boeing Service Bulletin 767-53-0078, Revision 
2, dated April 19, 2001; or Boeing Alert Service Bulletin 767-
53A0078, Revision 3, dated November 15, 2001; until paragraph (i), 
(l)(1), or (m) of this AD has been done.
    (1) Repeat the detailed inspection every 3,000 flight cycles, or 
18 months, whichever comes first.
    (2) Repeat the surface HFEC and LFEC inspections every 6,000 
flight cycles or 36 months, whichever comes first.

Repair and Follow-On Actions

    (h) If any cracking is found during any inspection required by 
paragraph (f) or (g) of this AD, before further flight, repair per 
paragraph (h)(1) or (h)(2) of this AD, as applicable.
    (1) For cracking of the aft outer chord, aft mid chord, or any 
intercostal: Repair per a method approved by the Manager, Seattle 
Aircraft Certification Office (ACO), FAA. For a repair method to be 
approved by the Manager, Seattle ACO, as required by this

[[Page 30620]]

paragraph, the Manager's approval letter must specifically reference 
this AD.
    (2) For cracking of the forward outer chord: Repair per Boeing 
Service Bulletin 767-53-0078, Revision 2, dated April 19, 2001; 
Boeing Alert Service Bulletin 767-53A0078, Revision 3, dated 
November 15, 2001; or Revision 4, dated September 26, 2002; except 
as provided by paragraph (j) of this AD. Procedures for repair 
include open-hole HFEC inspections for cracking of certain fastener 
holes of the chord and longeron fitting, detailed inspections for 
cracking of adjacent structure, and installation of new chords, 
splices, fairings, and brackets. If the time-limited repair is done 
per the service bulletin, do a detailed inspection of the repaired 
area within 1,500 flight cycles or 9 months after installation of 
the temporary repair, whichever comes first, and do paragraph 
(h)(2)(i) or (h)(2)(ii) of this AD, per the service bulletin. As of 
the effective date of this AD, inspect only in accordance with 
Boeing Alert Service Bulletin 767-53A0078, Revision 4, dated 
September 26, 2002.
    (i) If no cracking is found during the inspection of the 
repaired area: Within 3,000 flight cycles or 18 months after 
installation of the time-limited repair, whichever comes first, do 
paragraph (i), ``Permanent Repair,'' of this AD.
    (ii) If any cracking is found during the inspection of the 
repaired area: Before further flight, do paragraph (i), ``Permanent 
Repair,'' of this AD.

Permanent Repair

    (i) Except as provided by paragraph (j) of this AD, installation 
of the permanent repair of the forward outer chord, including 
accomplishment of all actions specified in Part 4 of the 
Accomplishment Instructions of Boeing Service Bulletin 767-53-0078, 
Revision 2, dated April 19, 2001; Boeing Alert Service Bulletin 767-
53A0078, Revision 3, dated November 15, 2001; or Boeing Alert 
Service Bulletin 767-53A0078, Revision 4, dated September 26, 2002; 
terminates the repetitive inspections required by paragraph (g) of 
this AD. As of the effective date of this AD, install the permanent 
repair only in accordance with Boeing Alert Service Bulletin 767-
53A0078, Revision 4, dated September 26, 2002.

    Note 2: Installation of the permanent repair before the 
effective date of this AD in accordance with Boeing Service Bulletin 
767-53-0078, dated October 15, 1998; Revision 1, dated September 9, 
1999; is acceptable for compliance with paragraph (i) of this AD.

Exception To Repair Instructions

    (j) For repairs of the forward outer chord: Where the service 
bulletin specifies to ask Boeing for repair data, repair per a 
method approved by the Manager, Seattle ACO, or per data meeting the 
type certification basis of the airplane approved by a Boeing 
Company Designated Engineering Representative who has been 
authorized by the Manager, Seattle ACO, to make such findings. For a 
repair method to be approved by the Manager, Seattle ACO, as 
required by this paragraph, the repair must meet the certification 
basis of the airplane, and the Manager's approval letter must 
specifically reference this AD.

New Requirements of This AD

Initial and Repetitive Inspections, and Torque Test for Airplanes 
Without the Permanent Repair

    (k) For airplanes that have not had the permanent repair 
installed in accordance with paragraph (i) of this AD, at the later 
of the times in paragraphs (k)(1) and (k)(2) of this AD, do all the 
actions in paragraph (l) of this AD.
    (1) Within 3,000 flight cycles or 18 months after the effective 
date of this AD, whichever occurs first.
    (2) Prior to the accumulation of 8,000 total flight cycles.
    (l) Do all the actions in paragraphs (l)(1) and (l)(2) of this 
AD in accordance with ``Part 1--Inspection'' of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 767-53A0078, Revision 
4, dated September 26, 2002.
    (1) Do a detailed inspection and applicable special detailed 
inspections (i.e., using LFEC and HFEC methods) for cracking of the 
forward and aft outer chord, splice fitting, aft mid chord, aft 
intercostal, tension fitting, and fuselage skin, and repeat the 
applicable inspections at the applicable time in paragraph (l)(1)(i) 
and (l)(1)(ii) of this AD. This inspection terminates the repetitive 
inspections required by paragraphs (f) and (g) of this AD.

    Note 3: For the purposes of this AD, a special detailed 
inspection is: ``An intensive examination of a specific item, 
installation, or assembly to detect damage, failure, or 
irregularity. The examination is likely to make extensive use of 
specialized inspection techniques and/or equipment. Intricate 
cleaning and substantial access or disassembly procedure may be 
required.''

    (i) Repeat the inspections, except for the open-hole 
inspections, at intervals not to exceed 3,000 flight cycles until 
the permanent repair in paragraph (m)(2) of this AD has been done.
    (ii) For airplanes that meet the criteria in flag note 1 of 
Figure 1 of Boeing Alert Service Bulletin 767-53A0078, Revision 4, 
dated September 26, 2002 (close ream fasteners, external doubler, 
rub strip, or wear plate installed): Repeat the open-hole HFEC 
inspections for cracking of the forward outer chord, splice fitting, 
tension fitting, and fuselage skin in Step 7, Figure 2, of the 
service bulletin at intervals not to exceed 9,000 flight cycles 
until the permanent repair in paragraph (m)(2) of this AD has been 
done. The open-hole HFEC inspections are required in addition to the 
surface inspections (HFEC, LFEC, and detailed visual inspections) 
required by paragraph (l)(1)(i) of this AD.
    (2) Do a one-time torque test and related investigative and 
corrective actions of the tension bolt at lower stringer 12A. If any 
corrosion or damage is found in the bolt hole, and the service 
bulletin specifies to contact Boeing for appropriate action: Before 
further flight, repair per a method approved by the Manager, Seattle 
Aircraft Certification Office (ACO), FAA; or per data meeting the 
type certification basis of the airplane approved by an Authorized 
Representative for the Boeing Delegation Option Authorization 
Organization who has been authorized by the Manager, Seattle ACO, to 
make those findings. For a repair method to be approved, the repair 
must meet the certification basis of the airplane, and the approval 
must specifically refer to this AD.

Corrective Actions

    (m) If any cracking is found during any inspection required by 
paragraph (l), (n) and (o) of this AD, before further flight, repair 
in accordance with paragraph (m)(1) or (m)(2) of this AD, as 
applicable.
    (1) For cracks found during the inspection required by paragraph 
(n) or (o) of this AD, or for cracks found in the aft outer chord, 
tension fitting, splice fitting, aft mid chord, or any intercostal: 
Before further flight, repair per a method approved by the Manager, 
Seattle ACO; or per data meeting the type certification basis of the 
airplane approved by an Authorized Representative for the Boeing 
Delegation Option Authorization Organization who has been authorized 
by the Manager, Seattle ACO, to make those findings. For a repair 
method to be approved, the repair must meet the certification basis 
of the airplane, and the approval must specifically refer to this 
AD.
    (2) For cracks in the forward outer chord: Prior to further 
flight, do the time limited repair in paragraph (h)(2) of this AD, 
or do the permanent repair in paragraph (i) of this AD. If the time 
limited repair is done, do the other applicable actions in paragraph 
(h)(2) of this AD at the times specified in that paragraph. As of 
the effective date of this AD, only repairs done per Boeing Alert 
Service Bulletin 767-53A0078, Revision 4, dated September 26, 2002, 
are acceptable for compliance with the requirements of this 
paragraph.

Repetitive Inspection of Repaired Area

    (n) For any airplane on which the permanent repair in paragraph 
(i) or (m)(2) of this AD is installed, at the latest of the times in 
paragraphs (n)(1), (n)(2), and (n)(3) of this AD: Do detailed, LFEC, 
and applicable HFEC inspections of the forward and aft outer chords, 
tension fitting, splice fitting, and splice angle for cracks; and a 
detailed inspection of the aft mid chord and aft upper and lower 
intercostals for cracks. Do the inspections in accordance with 
``Part 6--After Modification or After-Repair Inspection Program'' of 
the Accomplishment Instructions of Boeing Alert Service Bulletin 
767-53A0078, Revision 4, dated September 26, 2002. Repeat each 
inspection, except as provided by paragraph (o) of this AD, 
thereafter at intervals not to exceed 6,000 flight cycles, or 36 
months, whichever occurs first.
    (1) Within 12,000 flight cycles or 72 months, whichever occurs 
first, after the repair accomplished in accordance with paragraph 
(i) or (m)(2) of this AD.
    (2) Prior to the accumulation of 25,000 total flight cycles.
    (3) Within 18 months after the effective date of this AD.
    (o) For any airplane on which the permanent repair in paragraph 
(i) or (m)(2) of

[[Page 30621]]

this AD is installed, and that meets the criteria (close ream 
fasteners, external doubler, rub strip or wear plate installed) in 
flag note 1 of Figure 9 of Boeing Alert Service Bulletin 767-
53A0078, Revision 4, dated September 26, 2002: After the initial 
inspection in paragraph (n) of this AD, repeat the open-hole HFEC 
inspection in Step 7 of Figure 10 of the service bulletin, at 
intervals not to exceed 12,000 flight cycles, or 72 months, 
whichever occurs first. The open-hole HFEC inspections are required 
in addition to the surface inspections (HFEC, LFEC, and detailed 
visual inspections) required by paragraph (n) of this AD.

Alternative Methods of Compliance

    (p)(1) In accordance with 14 CFR 39.19, the Manager, Seattle 
ACO, is authorized to approve alternative methods of compliance 
(AMOCs) for the corresponding provisions of this AD.
    (2) AMOCs approved previously per AD 2001-09-13, amendment 39-
12220, are approved as AMOCs with the corresponding provisions of 
this AD.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD, if it is approved by an 
Authorized Representative for the Boeing Delegation Option 
Authorization Organization who has been authorized by the Manager, 
Seattle ACO, to make such findings.

Material Incorporated by Reference

    (q) Unless otherwise specified in this AD, the actions must be 
done in accordance with Boeing Service Bulletin 767-53-0078, 
Revision 2, dated April 19, 2001; Boeing Alert Service Bulletin 767-
53A0078, Revision 3, dated November 15, 2001; and Boeing Alert 
Service Bulletin 767-53A0078, Revision 4, dated September 26, 2002; 
as applicable.
    (1) The incorporation by reference of Boeing Alert Service 
Bulletin 767-53A0078, Revision 3, dated November 15, 2001; and 
Boeing Alert Service Bulletin 767-53A0078, Revision 4, dated 
September 26, 2002; is approved by the Director of the Federal 
Register, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) The incorporation by reference of Boeing Service Bulletin 
767-53-0078, Revision 2, dated April 19, 2001, was approved 
previously by the Director of the Federal Register as of May 24, 
2001 (66 FR 23538, May 9, 2001).
    (3) To get copies of the service information, contact Boeing 
Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207. 
You may view the AD docket at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street SW., room PL-401, 
Nassif Building, Washington, DC. To review copies of the service 
information, go to the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on May 16, 2005.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-10433 Filed 5-26-05; 8:45 am]
BILLING CODE 4910-13-P